Computer Science – Performance
Scientific paper
Sep 1992
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992lbsa.conf...35p&link_type=abstract
In NASA. Johnson Space Center, The Second Conference on Lunar Bases and Space Activities of the 21st Century, Volume 1 p 35-45 (
Computer Science
Performance
Electric Propulsion, Hydrogen Oxygen Engines, Lunar Bases, Lunar Flight, Lunar Spacecraft, Propulsion System Performance, Space Transportation, Cargo, Costs, High Impulse, Ion Propulsion, Manned Spacecraft, Orbit Transfer Vehicles, Plasma Propulsion, Propulsion System Configurations, Specific Impulse
Scientific paper
Using electric propulsion to deliver materials to lunar orbit for the development and construction of a lunar base was investigated. Because the mass of the base and its life-cycle resupply mass are large, high specific impulse propulsion systems may significantly reduce the transportation system mass and cost. Three electric propulsion technologies (arcjet, ion, and magnetoplasmadynamic (MPD) propulsion) were compared with oxygen/hydrogen propulsion for a lunar base development scenario. Detailed estimates of the orbital transfer vehicles' (OTV's) masses and their propellant masses are presented. The fleet sizes for the chemical and electric propulsion systems are estimated. Ion and MPD propulsion systems enable significant launch mass savings over O2/H2 propulsion. Because of the longer trip time required for the low-thrust OTV's, more of them are required to perform the mission model. By offloading the lunar cargo from the manned O2/H2 OTV missions onto the electric propulsion OTV's, a significant reduction of the low Earth orbit (LEO) launch mass is possible over the 19-year base development period.
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